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  • 1
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    Effect of lift-to-drag ratio in pilot rating of the HL-20 landing task (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: A man-in-the-loop simulation study of the handling qualities of the HL-20 lifting-body vehicle was made in a fixed-base simulation cockpit at NASA Langley Research Center. The purpose of the study was to identify and substantiate opportunities for improving the original design of the vehicle from a handling qualities and landing performance perspective. Using preliminary wind-tunnel data, a subsonic aerodynamic model of the HL-20 was developed. This model was adequate to simulate the last 75-90 s of the approach and landing. A simple flight-control system was designed and implemented. Using this aerodynamic model as a baseline, visual approaches and landings were made at several vehicle lift-to-drag ratios. Pilots rated the handling characteristics of each configuration using a conventional numerical pilot-rating scale. Results from the study showed a high degree of correlation between the lift-to-drag ratio and pilot rating. Level 1 pilot ratings were obtained when the L/D ratio was approximately 3.8 or higher.
    Keywords: SPACE TRANSPORTATION
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 30; 5; p. 543-548.
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    High-Alpha Research Vehicle (HARV) longitudinal controller: Design, analyses, and simulation resultss (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper describes the design, analysis, and nonlinear simulation results (batch and piloted) for a longitudinal controller which is scheduled to be flight-tested on the High-Alpha Research Vehicle (HARV). The HARV is an F-18 airplane modified for and equipped with multi-axis thrust vectoring. The paper includes a description of the facilities, a detailed review of the feedback controller design, linear analysis results of the feedback controller, a description of the feed-forward controller design, nonlinear batch simulation results, and piloted simulation results. Batch simulation results include maximum pitch stick agility responses, angle of attack alpha captures, and alpha regulation for full lateral stick rolls at several alpha's. Piloted simulation results include task descriptions for several types of maneuvers, task guidelines, the corresponding Cooper-Harper ratings from three test pilots, and some pilot comments. The ratings show that desirable criteria are achieved for almost all of the piloted simulation tasks.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-3446 , L-17323 , NAS 1.60:3446
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Launch-pad abort capabilities of the HL-20 lifting body (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The capability of the HL-20 lifting body to perform an abort maneuver from the launch pad to a horizontal landing was studied. The study involved both piloted and batch simulation models of the vehicle. A point-mass model of the vehicle was used for trajectory optimization studies. The piloted simulation was performed in the Langley Visual/Motion Simulator in the fixed-base mode. A candidate maneuver was developed and refined for the worst-case launch-pad-to-landing-site geometry with an iterative procedure of off-line maneuver analysis followed by piloted evaluations and heuristic improvements to the candidate maneuver. The resulting maneuver demonstrates the launch-site abort capability of the HL-20 and dictates requirements for nominal abort-motor performance. The sensitivity of the maneuver to variations in several design parameters was documented.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-4550 , L-17330 , NAS 1.15:4550
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    NASA TECHNICAL REPORTS
  • 4
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    Piloted simulator studies of the HL-20 Lifting Body (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: An overview is presented of the concept, design and development of the NASA Langley Lifting Body, and the flight simulator studies that have been performed. Attention is given to the aerodynamic shape of the HL-20, vehicle and simulator/cockpit description, and evolution of the HL-20 aerodynamic model. The flight simulation studies have demonstrated the HL-20 to be a viable design for accomplishing precise, unpowered, horizontal landings.
    Keywords: SPACE TRANSPORTATION
    Type: SETP Symposium; Sept. 26-28, 1991; Beverly Hills, CA; United States
    Format: text
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  • 5
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    Flight-Simulated Launch-Pad-Abort-to-Landing Maneuvers for a Lifting Body (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results of an in-flight investigation of the feasibility of conducting a successful landing following a launch-pad abort of a vertically-launched lifting body are presented. The study attempted to duplicate the abort-to-land-ing trajectory from the point of apogee through final flare and included the steep glide and a required high-speed, low-altitude turn to the runway heading. The steep glide was flown by reference to ground-provided guidance. The low-altitude turn was flown visually with a reduced field- of-view duplicating that of the simulated lifting body. Results from the in-flight experiment are shown to agree with ground-based simulation results; however, these tests should not be regarded as a definitive due to performance and control law dissimilarities between the two vehicles.
    Keywords: Ground Support Systems and Facilities (Space)
    Type: AIAA Paper 98-4254 , Atmospheric Flight Mechanics Conference; Aug 10, 1998 - Aug 12, 1998; Boston, MA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    NASA wake vortex research (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: NASA is conducting research that will enable safe improvements in the capacity of the nation's air transportation system. The wake-vortex hazard is a factor in establishing the minimum safe spacing between aircraft during landing and takeoff operations and, thus, impacts airport capacity. The ability to accurately model the wake hazard and determine safe separation distances for a wide range of aircraft and operational scenarios may provide the basis for significant increases in airport capacity. Current and planned NASA research is described which is focused on increasing airport capacity by safely reducing wake-hazard-imposed aircraft separations through advances in a number of technologies including vortex motion and decay prediction, vortex encounter modeling, wake-vortex hazard characterization, and in situ flow sensing.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AIAA PAPER 93-4004 , AIAA, Aircraft Design, Systems and Operations Meeting; Aug 11, 1993 - Aug 13, 1993; Monterey, CA; United States|; 12 p.
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Overview of the preparation and use of an OV-10 aircraft for wake vortex hazards flight experiments (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An overview is presented of the development, use, and current flight-test status of a highly instrumented North American Rockwell OV-10A Bronco as a wake-vortex-hazards research aircraft. A description of the operational requirements and measurements criteria, the resulting instrumentation systems and aircraft modifications, system-calibration and research flights completed to date, and current flight status are included. These experiments are being conducted by the National Aeronautics and Space Administration as part of an effort to provide the technology to safely improve the capacity of the nation's air transportation system and specifically to provide key data in understanding and predicting wake vortex decay, transport characteristics, and the dynamics of encountering wake turbulence. The OV-10A performs several roles including meteorological measurements platform, wake-decay quantifier, and trajectory-quantifier for wake encounters. Extensive research instrumentation systems include multiple airdata sensors, video cameras with cockpit displays, aircraft state and control-position measurements, inertial aircraft-position measurements, meteorological measurements, and an on-board personal computer for real-time processing and cockpit display of research data. To date, several of the preliminary system check flights and two meteorological-measurements deployments have been completed. Several wake encounter and wake-decay-measurements flights are planned for the fall of 1995.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA-TM-111259 , NAS 1.15:111259 , AIAA PAPER 95-3935 , NIPS-96-07977 , AIAA Aircraft Engineering, Technology, and Operations Congress; Sep 19, 1995 - Sep 21, 1995; Los Angeles, CA; United States
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    NASA TECHNICAL REPORTS
  • 8
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    Flight Investigation of the Effects of Pressure-Belt Tubing Size on Measured Pressure Distributions (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The pressure-belt technique is commonly used to measure pressure distributions on lifting and nonlifting surfaces where flush, through-the-surface measurements are not possible. The belts, made from strips of small-bore, flexible plastic tubing, are surface-mounted by a simple, nondestructive method. Additionally, the belts require minimal installation time, thus making them much less costly to install than flush-mounted pressure ports. Although pressure belts have been used in flight research since the early 1950s, only recently have manufacturers begun to produce thinner, more flexible tubing, and thin, strong adhesive tapes that minimize the installation-induced errors on the measurement of surface pressures. The objective of this investigation was to determine the effects of pressure-belt tubing size on the measurement of pressure distributions. For that purpose, two pressure belts were mounted on the right wing of a single-engine, propeller-driven research airplane. The outboard pressure belt served as a baseline for the measurement and the comparison of effects. Each tube had an outer diameter (OD) of 0.0625 in. The inboard belt was used to evaluate three different tube sizes: 0.0625-, 0.1250-, and 0.1875-in. OD. A computational investigation of tube size on pressure distribution also was conducted using the two-dimensional Multielement Streamtube Euler Solver (MSES) code.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM-2001-209857 , L-18078 , NAS 1.15:209857
    Format: application/pdf
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  • 9
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    Simulation Study of Flap Effects on a Commercial Transport Airplane in Upset Conditions (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: As part of NASA's Aviation Safety and Security Program, a simulation study of a twinjet transport airplane crew training simulation was conducted to address fidelity for upset or loss of control conditions and to study the effect of flap configuration in those regimes. Piloted and desktop simulations were used to compare the baseline crew training simulation model with an enhanced aerodynamic model that was developed for high-angle-of-attack conditions. These studies were conducted with various flap configurations and addressed the approach-to-stall, stall, and post-stall flight regimes. The enhanced simulation model showed that flap configuration had a significant effect on the character of departures that occurred during post-stall flight. Preliminary comparisons with flight test data indicate that the enhanced model is a significant improvement over the baseline. Some of the unrepresentative characteristics that are predicted by the baseline crew training simulation for flight in the post-stall regime have been identified. This paper presents preliminary results of this simulation study and discusses key issues regarding predicted flight dynamics characteristics during extreme upset and loss-of-control flight conditions with different flap configurations.
    Keywords: Aeronautics (General)
    Type: AIAA Paper 2005-5908 , AIAA Guidance, Navigation, and Control Conference and Exhibit; Aug 15, 2005 - Aug 18, 2005; San Francisco, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Dynamics Modeling and Simulation of Large Transport Airplanes in Upset Conditions (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: As part of NASA's Aviation Safety and Security Program, research has been in progress to develop aerodynamic modeling methods for simulations that accurately predict the flight dynamics characteristics of large transport airplanes in upset conditions. The motivation for this research stems from the recognition that simulation is a vital tool for addressing loss-of-control accidents, including applications to pilot training, accident reconstruction, and advanced control system analysis. The ultimate goal of this effort is to contribute to the reduction of the fatal accident rate due to loss-of-control. Research activities have involved accident analyses, wind tunnel testing, and piloted simulation. Results have shown that significant improvements in simulation fidelity for upset conditions, compared to current training simulations, can be achieved using state-of-the-art wind tunnel testing and aerodynamic modeling methods. This paper provides a summary of research completed to date and includes discussion on key technical results, lessons learned, and future research needs.
    Keywords: Aircraft Stability and Control
    Type: AIAA Paper 2005-5933 , AIAA Guidance, Navigation, and Control Conference and Exhibit; Aug 15, 2005 - Aug 18, 2005; San Francisco, CA; United States
    Format: application/pdf
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